Electro-optical triangulation rangefinder for contour measurement

ABSTRACT

A non-contacting, electro-optical system adapted automatically to measure the contour of a shaped object held in a fixture with its contoured surface presented to an electro-optical triangulation rangefinder assembly. The assembly is constituted by a pivoted laser beam illuminator and a pivoted automatic tracker mounted for rotation at spaced pivot points on a supporting beam, the line extending between these points forming a triangulation baseline. The illuminator is caused to swing through a sector whereby the laser beam spot scans across the surface of the object being tested from one edge to the other. The angles assumed by the illuminator and those assumed by the tracker in the course of a scan are determined and fed to a computer in which the value of the baseline is stored, the computer calculating the changing spot location by triangulation.

The U.S. Government (Department of the Army) holds a non-exclusiveroyalty-free license to this patent application.

RELATED APPLICATION

This application is a division of our pending application Ser. No.014,855, filed Feb. 23, 1979, now U.S. Pat. No. 4,226,536 entitled"Electro-Optical Contour Measuring System."

BACKGROUND OF INVENTION

1. Field of Invention

This invention relates generally to a non-contacting, electro-opticalmeasuring system for mapping the contoured surface of an object beingtested, such as the contour of a helicopter rotor blade, and moreparticularly to a system of this type which makes use of anelectro-optical triangulation rangefinder assembly to effect accurateand rapid contour measurements.

2. Prior Art

Though the invention is applicable to contour measurement of anythree-dimensional surface without making contact with the surface beingmeasured, we shall for purposes of explanation describe the invention inconnection with contour measurement of helicopter rotor blade surfaces.Such blades are relatively massive and present particular problems whichare solved by the present invention.

The performance of a helicopter and its operating life are greatlyaffected by the extent to which the rotor blades adhere to predeterminedcontour design requirements. If the manufactured blade deviatessignificantly therefrom, the rotating blade is subject to vibrationwhich not only degrades the performance of the vehicle in flight, butalso reduces the life of the blade and the gear box associatedtherewith.

The manufacture of many precision parts such as instrumentationcomponents and various shaped turbine and propeller blades, entailsclose control of and the ability to determine the contour of varioussurfaces on these parts. Conventional gauging systems for this purposemake use of contact probes that physically engage the surface underobservation to carry out the required contour measurement. To a largedegree, the accuracy of these measurements depends upon the stability ofthe mechanical structure which serves as a reference, for any twisting,bending or settling of the structure that takes place after themeasuring gauge is calibrated or in the course of measurement willadversely affect the accuracy of the reading.

When the object being measured is a helicopter blade, contact probesmust cover over 40 feet in the span direction and 48 inches in the chorddirection with a position accuracy of better than plus or minus 0.001inches under normal shop conditions. The cost and complexity of amechanical X-Y carriage for orienting a contour measuring probe withthis order of accuracy is exceptionally high. If multiprobes are used,the relative position of one to the other must be known and held tobetter than plus or minus 0.001 inches. This too is very expensive torealize in practice. Moreover, contact probes are subject to wear andmust be replaced at fairly frequent intervals.

Another practical drawback of conventional contact-type contour gaugingsystems is that they afford little, if any, flexibility in operation.Once the probes are positioned for a certain type of blade, before anyother blade configuration can be measured, a costly probe rearrangementis entailed.

To effect contour mapping of shaped objects, it is also known to usenon-contact, electro-optical systems such as those described in theWaters U.S. Pat. No. 3,909,131; the Lowrey et al. U.S. Pat. No.3,986,774; the Erb U.S. Pat. No. 3,671,126 and the Zoot et al. U.S. Pat.No. 3,679,307. These prior patents describe electro-optical techniquesfor surface gauging and represent noncontacting optical conceptspredicated on geometrical relationships between a source of radiationand a detector.

The above-identified Waters patent is of particular interest; for theinvention disclosed in this patent is based on the principle that as afocused spot of radiation from a laser source is moved in discreteincrements across the surface being gauged, contour variations can bemeasured by triangulation, this being accomplished by electronicallyfollowing the position of an image of the spot on a detector array. Twomodes of operation are disclosed by Waters. In one mode, the objectbeing tested is translated until the imaged spot is driven through anull position. In the other mode, it is the detector that is translatedrelative to the object.

In a non-contacting system of the Waters type operating in the mode inwhich the contoured object is physically displaced with respect to thetriangulation system, this translation results in shifting masses whichact to flex and distort the system, thereby giving rise to significantmeasurement errors, particularly when contour mapping large surfacessuch as helicopter rotor blades.

Alternately, when Waters translates his detector, this translationgenerates optical and mechanical errors in rotational angle which aredifficult to calibrate or control. These drawbacks are acknowledged byWaters who recommends object translation as "a superior operational modefrom an accuracy consideration" (column 7, lines 24 and 25).

Also of interest are the following prior art patents relating tonon-contact electro-optical measuring systems: Nordqvist, U.S. Pat. No.3,655,990; Foster et al., 3,858,983; Zanoni, 3,768,910; Zanoni,3,847,485 and Zanoni, 3,907,439.

SUMMARY OF INVENTION

In view of the foregoing, the primary object of the present invention isto provide a low-cost and relatively simple non-contactingelectro-optical system adapted to automatically measure the surfacecontours of helicopter rotor blades and other shaped objects, whichmeasurement is carried out at high speed and with a high order ofaccuracy.

More particularly, an object of this invention is to provide a system ofthe above type in which a contoured surface is mapped by means of anelectro-optical rangefinder assembly operating on the triangulationprinciple, the assembly being mounted on a carriage that is movable in astepwise manner with respect to an object being measured which isfixedly held at a stable position by a fixture.

Also an object of the invention is to provide a carriage-mountedrangefinder assembly constituted by a pivoted laser beam illuminator anda pivoted automatic tracker mounted for rotation at spaced pivot pointson a carriage beam, the line extending between points forming atriangulation baseline. The major variables are the two measured angles,one between the optical axis of the illuminator and the baseline, andthe other between the optical axis of the tracker and the baseline.

An important aspect of the invention resides in the fact that theilluminator and tracker are balanced so that their centers of gravitylie on their axes of rotation. As a consequence, one encounters nomechanical distortion of the contour measuring system due to shiftingmass centroids as the illuminator and tracker are rotated.

A salient feature of a system according to the invention is that it iscapable of functioning in a factory or engineering environment toperform contour measurement on relatively large and massive objects suchas helicopter blades, with a speed and accuracy that represents anotable advance over prior techniques. Another advantage of theinvention is its inherent flexibility; for the same system may be usedto effect contour measurement of different types of blades withoutrearrangement--for all that is required when a different type of bladeis to be automatically contour-measured is operator control or softwarereprogramming.

Still another object of the invention is to provide a non-contactelectro-optical automatic contouring system in which flexure anddistortion in the translating carriage structure supporting therangefinder assembly is corrected by means of straight calibration barswhose mountings are mechanically independent of the rangefinder. Themechanical structure of the present system is less elaborate and costlythan structures heretofore required, in that the requirements fordimensional stability are reduced to a considerable degree due to theself-calibration feature.

Yet another object of the invention is to provide a two-stage trackerangle readout in which the tracker angle used in calculating the contouris the algebraic sum of an angle measured electromechanically over anangular range of ±30° to an accuracy of one second and an angle measuredelectro-optically over an angular range of ±0.1° to an accuracy of onesecond, thereby affording both fine and coarse measurements.

Briefly stated, in a system in accordance with the invention whenarranged to effect contour measurement of a helicopter rotor blade, theblade is supported in a stable position by a fixture which holds theblade with its leading and trailing edges placed between upper and lowerflat calibration bars.

In order to carry out contour-measurement concurrently on both contouredsides of the fixture-supported helicopter blade, a gantry-like carriageis provided which rides on rails that straddle the fixture, the carriageincluding a pair of vertical beams on opposing sides of the blade andequi-spaced from the chord thereof.

Supported at corresponding positions on these beams are two likerangefinder assemblies, each assembly being constituted by a pivotedlaser beam illuminator and a pivoted automatic tracker mounted forrotation on the associated beam on spaced pivot points, the lineextending between the pivot points representing a triangulationbaseline. The illuminator and tracker are each counterbalanced tomaintain fixed centroids.

The carriage is caused to step incrementally along the rails from oneend of the blade to the other. At each carriage step, the rangefinderassemblies are both activated, to cause each illuminator to swingthrough a sector whereby the laser beam spot impinging on the bladescans across the related surface from the leading to the trailing edgethereof. Means associated with each assembly act to determine thechanging angles assumed by the illuminator and those assumed by thetracker in the course of a scan, these angular values being fed to acomputer in which the baseline value is stored, the computer calculatingthe changing location of the spot by triangulation.

This scanning operation, which takes place simultaneously on both sidesof the blade, is repeated at every carriage step from one end of theobject to the other, thereby mapping the entire contour of bothsurfaces. At the beginning and end of each contour scan, the rangefinderassemblies are calibrated by contouring the flat calibration barslocated adjacent the leading and trailing edges of the blades, so as tointroduce a correction factor taking into account any mechanicaldistortion of the rangefinder position resulting from carriage movementalong the rails.

OUTLINE OF DRAWINGS

For a better understanding of the invention as well as other objects andfurther features thereof, reference is made to the following detaileddescription to be read in conjunction with the accompanying drawings,wherein:

FIG. 1 is a perspective view of a non-contacting electro-optical contourmeasuring system in accordance with the invention, the system beingarranged to carry out contour mapping of opposing surfaces of ahelicopter rotor blade by means of a pair of rangefinder assemblies;

FIG. 2 is an enlarged perspective view of one of the rangefinderassemblies;

FIG. 3 shows a portion of a helicopter rotor blade to be tested;

FIG. 4 is a schematic diagram of the measuring system;

FIG. 5 is a block diagram of the measuring system; and

FIG. 6 is a block diagram of the fine angle tracker.

DETAILED DESCRIPTION OF INVENTION System Structure

Referring now to FIG. 1, there is shown a fixture for supporting ahelicopter rotor blade 10 lengthwise at a stable position suitable forcontour mapping by a non-contacting electro-optical measuring system inaccordance with the invention, which system includes a pair oftriangulation rangefinder assemblies, one for each side of the blade.

Rotor blade 10, by way of example, has a length of 40 feet and a chordof 48 inches. As best seen in FIG. 3, chord C is a straight line joiningthe leading edge L of blade 10 which has an airfoil shape, to thetrailing edge T thereof. The blade possesses contoured front and rearsurfaces S₁ and S₂ whose contours are to be mapped to determine whetherthey conform to predetermined design requirements and, if not, theextent to which they deviate therefrom.

The fixture for supporting the blade lengthwise is constituted by aframe-shaped bed or base 11 which rests on or is bolted to the floor andis level therewith, the base including a pair of parallel girders 11Aand 11B. Placed between these girders and mounted at spaced positions ontransverse ties 12 which bridge the girders are a series of uprights13A, 13B, 13C etc.

Each upright, such as upright 13C, is provided with a pair of spacedupper and lower cantilever arms 14 and 15 whose ends are equipped withclamps 14C and 15C adapted to grip the trailing and leading edges,respectively, of the blade. The number of uprights and their spacing aresuch as to securely support the blade being tested so that its positionis stationary and remains so in the course of testing.

Also supported by the upper cantilever arms 14 of the uprights is ahorizontally-extending calibration bar 16 having a narrow flathorizontal edge, the bar extending the full length of the blade.Supported below the lower cantilever arms 15 of the uprights on uprightbracket 17 is a horizontally-extending calibration bar 18 also having asimilar edge.

Thus the fixture locates the blade between two reference bars whichestablish the coordinate system for contour measurement. In practice,therefore, the means to position the electro-optical rangefinder neednot be controlled, say, to plus or minus 0.001 inches relative to therotor blade, the only requirements being that its position be known toplus or minus 0.001 inches as determined by scanning the reference bars.

Since the series of uprights optically obscure side S₂ of the blade, theuprights are made in a narrow width consistent with structuralrequirements to minimize this effect and to maximize the exposure ofside S₂ to the electro-optical rangefinder which scans this side.

In practice, base 11 may be made in girder sections of suitable stocklength, so that the base is readily transportable and can be installedwithout difficulty. Standard couplers are used to join the girdersection together, means being also provided for levelling the entirelength of the base.

The optical sensor of the contour measuring system requires atransporting mechanism which moves the sensor spanwise along the bladebeing measured. This transporting mechanism is constituted by agantry-type carriage, generally designated by numeral 20, which rides ona pair of rails 21A and 21B resting on base girders 11A and 11B.

Carriage 20 includes a pair of parallel vertical beams 22A and 22B whosetop ends are bridged by a cross beam 23, the lower end of beam 22A beingjoined to a two-wheel truck 24 riding on rail 21A. The lower end of beam22B is joined to a single wheel truck (not shown) which rides on rail21B, thereby providing a stable, three-point suspension.

The length of the fixture base and of the rails thereon are at least 50feet so that carriage 20 can travel beyond and clear the 40-feet lengthrotor blade held on the fixture at either end of the blade to a degreesufficient to allow loading and unloading of blades to be tested.

As best seen in FIG. 2, pivotally mounted on a pad 25 secured tovertical beam 22A is a first rangefinder assembly I including laser beamilluminator 26 which is rotatable through sufficient angles to scan thesurface S₁ for the entire chord C; that is, from the leading to thetrailing edge of the blade. Pivotally mounted on a pad 27 secured tobeam 22A at a position above that of pad 25 is a tracker 28 which isrotatable through sufficient angles to intercept the illuminator beamreflected from surface S₁ of the blade. The straight line extendingbetween the pivot point or axis of illuminator 26 and the pivot point oftracker 28 represents the baseline of the triangulation rangefinder. Inone practical embodiment, this baseline is 40 inches long.

Laser beam illuminator 26 preferably generates a 0.001 inch by 0.100inch line image on the surface of the rotor blade, which image ishereafter referred to as the laser beam spot. In operation, illuminator26 is rotated about its pivot axis; and as the illuminator swings, thespot travels along the surface in the chord direction. Tracker 28captures the beam reflected from the spot position in its field of viewand tracks it as it travels across the chord.

The structure of the illuminator and the structure of the tracker areboth counterbalanced to minimize shifting of masses on the supportingframe of the measuring equipment, thereby improving measuring accuracyand reducing the cost and complexity of the supporting frame. Bycounterbalancing is meant that the structure of the tracker and that ofthe illuminator have a fixed mass distribution such that they arebalanced in the inactive state with respect to either side of the centerof gravity. There are only two small masses which shift in the course ofoperation, these being one focusing lens in the illuminator which ismotor-driven, and one in the tracker which is motor-driven. These massesshift only a few inches while making measurements and are continuouslycounterbalanced, so that there is no net shift.

Mounted on beam 22B at positions corresponding to illuminator 26 andtracker 28 of the first rangefinder assembly I is a second and identicalrangefinder assembly II for contour-measuring the S₂ side of the blade.The second assembly is constituted by a pivotally-mounted laser beamilluminator 26b' and a tracker 28' whose structure and function are thesame as those of illuminator 26 and tracker 28 of the first assembly.

Carriage 20 is motor-driven, as by means of an endless belt 29operatively coupled to beam 21B, to advance the carriage and therangefinder assemblies borne thereby in incremental steps from one endof the blade being measured to the other. When the carriage occupies agiven step, a scanning action is carried out concurrently on opposingsides of the blade by rangefinders I and II to determine the contours ofthe blade sides.

Thus, as shown in FIG. 3, at the first step, chord C is scanned at oneend of blade 10, then the carriage is incrementally advanced, and at thenext step Chord C₁ is scanned, this being repeated at chord C₂ and so onuntil the chord at the other end of the blade is reached and both sidesof the blades are contour mapped.

Because the leading edge L of the air-foil shaped blade has abullet-nosed formation and is inaccessible to the tracker, it cannotdirectly view the surface thereof. To facilitate tracking of the leadingedge, a mirror 30 is fixed to the rangefinder assembly at a positionbelow the leading edge L of the blade. The mirror is oriented tointercept the line-of-sight of the tracker and to redirect it to theleading edge of the blade. The mirror is positioned so that the areaaround the leading edge is fully visible to the tracker, starting fromthe area where the chordal plane intersects the rotor surface, andextending back along the rotor surface to the area which is directlyvisible to the tracker without the use of the mirror.

The location of the mirror surface must be determined relative to thetriangulation rangefinder, in order to make contour measurements bytracking through the mirror, and in order to relate these contourmeasurements to those made by tracking the rotor surface directly. Apreferred method for determining the mirror surface location usesilluminator angle and tracker angle measurements made on two points onthe rotor surface which are visible to the tracker both directly andthrough the mirror. The unique mirror position which is consistent withthese four pairs of angle measurements can then be determined bystandard algebraic methods.

Alternatively, a mirror can be used to redirect the flux from theilluminator onto the rotor surface, without deflecting the tracker'sline of sight. Two or more mirrors may be used for access to curvedsurfaces which are not directly visible to either the illuminator or thetracker.

System Operation

Referring now to FIGS. 4 and 5, it will be seen that rangefinderassemblies I and II of the contour measuring system are borne by beams22A and 22B, each assembly having an illuminator and a tracker inoperative relation to a respective side of rotor blade 10. Since the twoassemblies are identical, only the motors and other devices associatedwith rangefinder assembly I will be described in this section.

The incremental stepping of carriage 20 to advance the rangefinderassemblies through successive chords C, C₁, C₂ etc. from the front endto the rear end of the blade 10 being tested is effected by a carriagestepping motor 31 which drives belt 29. Motor 31 operates in conjunctionwith an encoder 32 that provides a signal indicative of the carriagestep position. This signal is supplied to a computer 33 which governsthe operation of the system and also acts in response to signalssupplied thereto by the rangefinder assemblies to carry out computationsbased on the sensed values in order to effect contour measurements bytriangulation.

In practice, computer 33 may be a general purpose microcomputer withsufficient speed and memory to handle all of the control functions ofthe contour measurement system as well as the necessary computationaland report-generating functions. Use may be made of a dual floppy-discsystem which is associated with the microcomputer to provide amplenonvolatile storage for measurement programs, blade specification dataand general purpose utility programs. Two independent disc drivers aresupplied so that discs may be copied for back-up to lessen the risk ofdowntime due to hardware failure.

The angular position of illuminator 26 of rangefinder assembly I iscontrolled by a scan motor 34 and that of automatic tracker 28 by a scanmotor 35 included in a servo system. One form of servo system suitablefor automatically controlling a tracker is disclosed in theabove-identified Nordqvist patent whose disclosure is incorporatedherein.

Illuminator 26 includes a focusing lens 36 controlled by a focus motor37 whose position is sensed by an encoder 37A. Tracker 28 includes afocusing lens 38 controlled by a focus motor 39 whose position is sensedby an encoder 39A. As the laser illuminator pivots, its beam ismaintained in focus on the surface of the rotor blade by a closed-loopcontrol system which acts to focus the output lens of the illuminator, asimilar focusing control system being included in the pivoting tracker.

The changing angular position of illuminator 26 in the course of a scanis sensed by an illuminator scan-sensor or encoder 40, and that of thetracker by a tracker scan-sensor or encoder 41. These changing angularvalues are fed to computer 33 wherein the known value of the baseline isstored. One commercially-available angle sensor suitable for thesepurposes is sold under the "Inductosyn" trademark.

The length of the baseline varies slightly as the illuminator angle andthe tracker angle change. This baseline variation is due to the factthat the optical axes of the illuminator and tracker do not, in general,exactly intersect their corresponding rotation axes, due toconstructional tolerances in making and assembling their components.

The illuminator and the tracker could, in principle, be designedincorporating adjustment mechanisms which would permit alignment oftheir components so that their optical axes would exactly intersecttheir rotation axes. However, a preferred system design is to measureand record the residual misalignments of these axes during systemcalibration, and then to calculate the small baseline corrections whichare required as part of the data reduction program used in contourmeasurement.

In order to contour the surface, illuminator 26 pivots so that the laserspot travels across that chord (C, C₁, C₂, C₃ etc.) which is inregistration with the existing step position at an angular rate of about3° per second. And as as the illuminator pivots, tracker 28 is caused toswing to track the laser spot under closed loop servo control, thisbeing accomplished in practice to a "coarse" accuracy of 0.050". Anopen-loop sensor located in the tracker (to be hereinafter described)determines the position of the laser spot to a "fine" accuracy of0.0005".

As rangefinder assemblies I and II are advanced by the carriagestep-by-step to carry out contour measurements on either side of therotor blade along the full length thereof, the 50-foot long rails onwhich the carriage travels will tend to settle and twist and therebyslightly alter the rangefinder orientation relative to the blade. Tocorrect for the resultant errors, the rangefinders are calibrated bycontouring the two flat reference bars 16 and 18 adjacent the leadingand trailing edges of the blade on the holding fixture. The angularorientation of the pivot axis is monitored by an auto collimatorconnected rigidly to the pivot axis, the auto collimator looking at afixed target on the blade-holding fixture.

In practice, the laser illuminator may be constituted by a helium-neonlaser source 42 emitting 5 milliwatts of polarized light at 0.6328micron wavelength in a 0.8 mm diameter beam with a 1 milliradian beamdivergence. The resultant light path is folded by flat mirrors M₁ and M₂(see FIG. 2) for system compactness, and its diameter is expanded sixtytimes by an optical beam expander 43 in order to reduce its divergencefrom 1000 microradians to 25 microradians. In the direction parallel tothe span axis, a hundred times larger beam divergence of 2500microradians is generated by a cylindrical lens incorporated in the beamexpander. The expander output is focused on the rotor surface by aservoed objective lens 36 so that it generates a 0.001 inch by 0.100inch line image.

The use of a spot having a line formation rather than a round formationis useful in contouring rough, somewhat cylindrical surfaces, such asthe fiberglass surface of a helicopter rotor blade. To this end, theilluminator beam expander incorporates an anamorphic lens which spreadsout the spot of light into a 0.001×0.100 inch line parallel to thelongitudinal axis of the rotor blade. This lens interacts with the rotorsurface to decohere the laser illumination, thereby reducing thetracker's speckle noise to a negligible level.

In practice, the amount of light collected by the tracker whencontouring a dark surface can be well under one microwatt. It isimportant, therefore, to be able to distinguish this significant lightfrom all ambient or stray illumination and thereby prevent the systemoutput from being distorted in the typical factory environment in whichrotor blades undergo contour measurement. To this end, the system inaccordance with the invention incorporates three distinct kinds offiltering which, taken together, render the electro-optical systemsubstantially immune to stray illumination that would otherwise bias thecontour reading.

The first filter is temporal in nature, this being accomplished by amodulator 44 interposed in the optical path between laser 42 and beamexpander 43, the beam being modulated at a repetition rate of 1,000 Hz.The tracker output is synchronously demodulated to be optimallysensitive to the modulated incoming flux and to reject the 120 and 60 Hzfrequencies commonly encountered in a-c powered factory light sources.

The second filter is spectral in character, in that the illuminatorlight output is concentrated at a spectral wavelength (0.6328 microns inthe case of radiation from a helium-neon laser). The tracker output iscorrespondingly optically filtered to restrict its response to a narrowbandwidth (i.e., ±0.005 microns in the helicopter rotor contouringsystem), which encompasses the selected spectral wavelength and rejectsother wavelengths. The third filter is spatial, and to this end thetracker is masked to receive radiation only from a field view ±1/4 incharound its aim point.

In the present system, the tracker angle used in contour calculation isthe algebraic sum of two angles, one being a course angle measuredelectromechanically by scan position encoder 41 over an angular range of±30° to an accuracy of one second of arc. This measurement may beeffected with a commercially-available angle sensor known as anInductosyn.

The other angle measurement used in contour calculation is a fine anglemeasurement carried out electro-optically by a fine tracker 45 over anangular range of ±0.1° to an accuracy of one second of arc. Thistwo-stage angle readout for the tracker tolerates leads or lags ofseveral minutes of arc in the tracker's optical axis, making it possibleto use a servoed tracker system which can follow an illuminated spotmoving at an angular rate of several degrees per second. The fine angletracker design provides an output voltage proportional to angle errorover a field of view of approximately six minutes.

As shown in FIG. 6, the fine angle tracker views the illuminatedline-shaped spot on the rotor surface S₁ through a lens systemcomprising a collimating objective lens 46 and a servoed-focusingobjective lens 47. A square aperture stop 48 is interposed between theselenses, with one pair of its sides parallel to the line image on therotor surface. A spectral filter 49 is placed in the optical path behindobjective lens 47.

The square aperture stop operates in conjunction with the objective andfocusing lenses to generate a square pyramid of light flux in thetracker. This pyramid converges toward a line-shaped apex parallel tothe same two sides of the aperture stop, the apex being an image of thelaser spot on the rotor surface.

The square pyramid of light is intercepted near its apex by atwo-element silicon photodetector 50. The output of detector 50 is fedthrough preamplifiers 51 and 52 to differential and summing amplifiers53 and 54 whose algebraically combined output is applied to a ratiocircuit 55, the output of which goes to a scaler 56 which yields thefine angle output reading.

The two-element silicon photodetector can be conveniently constructed byconnecting appropriate adjacent pairs of elements in acommercially-available quadrant-type four-element silicon detector. Theuse of a four-quadrant silicon detector is a preferred designconfiguration because it makes possible an alternate pairing of adjacentquadrants which facilitates leveling of the illuminator and tracker axesduring construction and alignment of the system.

The intersection of the photodetector plane with the flux pyramid is arectangle of light with an intensity distribution which is bilaterallysymmetrical. If the laser line moves off center in the field of view ofthe tracker, the ratio of the difference divided by the sum of the fluxlevels intercepted by the two silicon elements of detector 50 is adirect linear measure of the distance of the laser line from the centerof the tracker's field of view.

The optical geometry and detector configuration are important elementsof the system, for its metrological integrity depends on the feasibilityof establishing a stable relationship between the flux difference in thetwo detectors and the line position.

The advantage of a two-element silicon photodetector lies in the factthat these detectors exhibit responsivities which change only about0.1%/C°. Moreover, such two-element silicon detector elements havepractically identical chemical and physical properties and tend,therefore, to track their cellmates in photodetective responsivity.

In contradistinction, conventional photomultiplier detectors areindividually made and exhibit responsivities which change about 1%/C°.Hence it would be difficult to find two individual photomultipliers thatmatch in responsivity over the temperature range normally encounteredduring the expected lifetime of a contour measuring system of thepresent type.

The use of two angle measurements combined with one predetermined sidelength (baseline) enables the triangulation rangefinders I and II tocarry out contour measurement relative to the length of the baseline asthe single scaling factor. The length of the baseline which extendsbetween the illuminator and tracker pivot points on the supporting beamof the carriage is, of course, affected by the temperature coefficientof the supporting beam and therefore is dependent on temperature.However, the baseline is compact, so that its temperature is relativelyuniform, constant and easily monitored.

In a system in accordance with the invention, the contouring speed isfast because of the two-stage track angle readout. This two-stagereadout makes feasible on operating speed that is orders of magnitudemore rapid than is attainable with a one-stage system. In practice, theuse of a two-stage tracker, a high intensity laser beam illuminator andstate-of-the-art computer technology makes it possible to carry outmeasurement of a full contour line in less than one minute. During thisbrief interval, the baseline beam temperature changes less than ±0.1° F.which corresponds to a change in scale factor of less than one part in amillion.

Thus the two-stage tracker, the intense laser beam and advanced computertechnology taken in conjunction with a monolithic baseline constitute asynergistic combination and makes possible operation in a favorableregion of the temporal noise spectrum.

When contouring successive chords of the rotor blade, the triangulationrangefinder assemblies are translated in a step-wise manner by thecarriage on which these assemblies are borne relative to the opposingsurfaces of the blade. As noted previously, this causes twisting anddistortion in the structure supporting the rangefinder assemblies andslightly changes the orientation thereof relative to the surfaces. Sincethis distortion is corrected by the use of straight calibration bars 16and 18 mounted independently of the rangefinder assemblies, these barsmust be surveyed-in and adjusted for straightness so that they can serveas an invariant reference coordinate system to determine the orientationof the rangefinder assemblies after each step along the length of theblade.

Alternatively, the rangefinder can be rotated on a thirdInductosyn-monitored spindle axis which is oriented at right angles tothe two parallel pivot axes of the illuminator and the tracker. The useof this third rotary axis substitutes a balanced rotary motion with zerocentroid shift for the unbalanced translational motion and it obviatesthe need for calibration bars.

While there has been shown and described a preferred embodiment of anelectro-optical contour measuring system in accordance with theinvention, it will be appreciated that many changes and modificationsmay be made therein without, however, departing from the essentialspirit thereof. Thus instead of running the carriage transporting therangefinder assemblies I and II on ground rails, an overhead railarrangement for this purpose may be provided.

We claim:
 1. In a system for measuring the surface contour of a shapedobject, a triangulation range-finder assembly comprising:A. a supportingbeam at a position facing the surface to be measured: B. a light-beamilluminator pivotally mounted on said beam; said light beam beinggenerated by a laser beam source; and a beam expander including ananamorphic lens to spread out said laser beam to create a luminous spoton said surface having a fine line formation which is parallel to thelongitudinal axis of said object; C. an automatic tracker pivotallymounted on said beam at a point thereon spaced from the illuminatorpivot point to exactly define a triangulation baseline having a knownvalue extending between the pivot points; and said tracker having a twostate readout whose output is the algebraic sum of a course angle and afine angle tracker measurement; D. means to cause said illuminator toswing through a sector wherein said light beam impinges on a saidsurface to produce a luminous spot thereon that scans in a pathextending from one edge of said object to the other and to cause saidtracker in response to light reflected from said surface to follow saidscanning spot, said illuminator and said tracker having counterbalancedstructures to maintain fixed centroids on said beam, said system furtherincluding means operatively associated with said illuminator and saidtracker to determine the changing angular values assumed thereby in thecourse of a tracked scan; and a computer having said baseline valuestored therein and responsive to said changing angular values to computeby triangulation the changing location of said spot in the course ofsaid tracked scan and to thereby provide a reading of the contour ofsaid object in the path of the scan.